Prediction of the Nonlinear Aerodynamic Characteristics of Tandem-Control and Rolling-Tail Missiles

Lesieutre, Daniel J.; Love, John F.; Dillenius, M. F. E.

doi:10.2514/6.2002-4511

Cited by 19 publications

(9 citation statements)

References 4 publications

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“…Fluent is used throughout the aerospace industry as a research and design tool. Although it is semiempirical, it has been shown by a number of authors to compare favourably with experimental research (9)(10)(11)(12) . The use of computational fluid dynamics has been validated against MISL3 (6) and wind tunnel tests (7,8) .…”

Section: Methodsmentioning

confidence: 99%

Numerical investigation of optimal pin location on a supersonic projectile

Bell¹,

Robinson²,

Robinson³

2012

Aeronaut. j. (1968)

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The flowfield around a supersonic projectile using a pin actuator control method has been predicted using computational fluid dynamics. It has been predicted using both viscous and inviscid methods for a number of positions. Both methods showed that an optimal longitudinal position exists. However, the inviscid model over-predicted the lateral acceleration due to the difference in shock formation around the pin between the two approaches. The optimal location was predicted independent of solver, however the higher-fidelity solver predicted lower achievable lateral accelerations. This is due to the viscous interactions caused by the pin. The effect of projectile orientation has shown that shielding the pin leads to reduced effectiveness due to the wake of the fin enveloping the pin. When the pin is exposed to onset flow, the forces achieved are increased. There is also an increase in the achievable forces and moments with increasing Mach number.

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Section: Methodsmentioning

confidence: 99%

Numerical investigation of optimal pin location on a supersonic projectile

Bell¹,

Robinson²,

Robinson³

2012

Aeronaut. j. (1968)

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“…1,8 The test objective was to provide an aerodynamic database to study and evaluate tandem control effectiveness. The model consists of a 3-caliber ogive nose followed by a 12-caliber cylinder with cruciform inline canards and aft tail fins.…”

Section: Tandem Control Missile Modelmentioning

confidence: 99%

Studies of Vortex Interference Associated with Missile Configurations

Lesieutre

Quijano

2014

52nd Aerospace Sciences Meeting

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Studies of vortex-induced aerodynamic nonlinearities associated with body and fin vortices for missile configurations have been performed. As part of this effort, the vortex and fin modeling methodologies in the engineering-level and intermediate-level aerodynamic predictions codes MISL3 and MISDL have been reviewed and improved. The ability of the methods to predict detailed fin loads in the presence of external vortices is demonstrated. Both codes have been used extensively to predict missile performance including canard/wing vortex induced effects on tail fins. These effects often manifest themselves in pitching moments and most dramatically in induced rolling moments on tail fins which counter, and often times reverse, the direct roll control of canard fins. Both codes have shown the capability to capture these vortexinduced phenomena. For validation purposes, the methods were compared to detailed vortex-fin interaction studies, performed at Sandia National Laboratories, which measured fin loads influenced by a vortex generated by an upstream fin. Nomenclature AR= aspect ratio (two fins joined at root) C l = rolling moment/q ∞ S R l R C m = pitching moment/ q ∞ S R l R ; positive nose up C N = normal force/ q ∞ S R C NF = fin normal force/ q ∞ S R D = body diameter, maximum L = body length l R ,L REF = reference length q ∞ = freestream dynamic pressure S R ,S REF = reference area x CP = fin chordwise center of pressure, or overall configuration axial center of pressure y CP = fin spanwise center of pressure x HL = fin hinge line loaction x MC = moment center α = angle of attack, deg δ = fin deflection angle or angle of attack for fin alone, deg λ = fin taper ratio φ = roll angle, deg

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“…Previous research has shown that the VFI effects are critical to the performance of the munition because the downwash of the canard vortices can reduce the effectiveness of the tail fins with potentially detrimental effects [2,[9][10][11][12][13][14][15][16][17][18][19][20][21][22]. The interactions depend strongly on how the canards are deflected (i.e., for roll, pitch, or yaw control) and the angles of attack under consideration.…”

mentioning

confidence: 99%

“…Much of this research on the VFI has been conducted on the NASA Blair missile configuration at supersonic speeds [9,10] for a slender body (large length-to-diameter ratio) with canards and tail fins aligned in roll orientation. The results of the Blair wind-tunnel studies have been used to improve engineering-level and intermediate-level aerodynamic prediction codes [15][16][17], which use panel methods, vortex-cloud methods, or other semi-empirical methods to account for the vortices shed from the canards and body. The aerodynamic prediction codes give reasonable results over the parameters for which they have been validated and can model the flow interaction effects for a supersonic missile.…”

mentioning

confidence: 99%

Effect of Canard Interactions on Aerodynamic Performance of a Fin-Stabilized Projectile

Silton

Fresconi

2015

Journal of Spacecraft and Rockets

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This study was undertaken to better understand the impact of the canard trailing vortex flow interactions on the aerodynamic design and flight performance of short length-to-diameter, fin-stabilized munitions. Advanced computational aerodynamic and parameter sensitivity analysis techniques were applied. Results indicated that airframe designs that did not consider canard trailing vortex interactions on tail fins suffered from drastically underpredicted stability. Analyses were performed with the canard trailing-edge vortex-tail-fin interactions included to design a new airframe, and the suitability of this design was verified. The aerodynamics of the resulting configuration, as determined from advanced computational techniques, compared within 25% of the predictions (stability underpredicted) using scaled aerodynamic coefficients, suggesting that inclusion of scaled interference effects is a reasonable assumption during the design process. Nomenclature C l = roll moment coefficient C m = pitching moment coefficient referenced to configuration center of gravityof body coordinates D = reference diameter, m f c = canard scaling factor f F = fin scaling factor L∕D = lift-to-drag ratio M = Mach number x c = axial location of canard hinge location, caliber from X cg x c ref = axial location of canard hinge location at which the canard aerodynamic coefficients are determined. X cg = center of gravity location, mm y = nondimensional turbulent boundary-layer coordinate α = angle of attack, deg α trim = trim angle of attack, deg Δy = first cell spacing off wall, mm δ = canard deflection angle, deg Superscripts B = body C = canards F = tail fins

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Prediction of the Nonlinear Aerodynamic Characteristics of Tandem-Control and Rolling-Tail Missiles

Cited by 19 publications

References 4 publications

Numerical investigation of optimal pin location on a supersonic projectile

Numerical investigation of optimal pin location on a supersonic projectile

Studies of Vortex Interference Associated with Missile Configurations

Effect of Canard Interactions on Aerodynamic Performance of a Fin-Stabilized Projectile

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